Method for realizing fast moving of non-coplanar orbits by utilizing suspension orbit

A technology of orbital motion and orbit, applied in the field of orbital mechanics, can solve the problems that the time consumption of maneuvering missions exceeds the requirements of mission indicators, and the requirements for aircraft engine thrust capabilities are too high and cannot be realized.

Active Publication Date: 2016-10-26
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

However, this method has a fatal flaw. Since this maneuver is a pulsed maneuver or a continuous thrust maneuver in a short period of time obtained through transformation, this method is only suitable for small-scale orbital surface adjustment problems with small orbital surface angles. Aiming at the problem of large-scale different-plane orbital maneuvering in the usual sense, this method puts too high a demand on the thrust of the aircraft engine, and the existing technology cannot realize it at all.
In addition, due to the independent adjustment of the orbit plane and phase angle in this method, considering the limitations of the phase modulation orbit height and phase modulation pulse, the phase modulation phase cannot be guaranteed to be completed within a single orbit cycle, so in some cases the time consumption of maneuvering tasks may also be Far beyond the task index requirements

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  • Method for realizing fast moving of non-coplanar orbits by utilizing suspension orbit
  • Method for realizing fast moving of non-coplanar orbits by utilizing suspension orbit
  • Method for realizing fast moving of non-coplanar orbits by utilizing suspension orbit

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Embodiment Construction

[0067] The present invention is described in further detail below in conjunction with accompanying drawing:

[0068] see Figure 1-Figure 12 , the present invention utilizes the suspended track to realize the rapid maneuvering method of different plane tracks, comprising the following steps:

[0069] Step 1. Maneuvering Process Planning

[0070] This patent proposes the application of the suspension orbit as a transition orbit in the rapid maneuvering of different plane orbits. The suspension orbit (displaced orbit) is usually defined as under the two-body assumption, through the action of external force, so that the orbit plane does not pass through the earth (or other central gravitational force) body) a non-Kepler orbit of the center of the sphere, such as figure 1 shown. Here, the initial orbit, the target orbit and the suspension orbit are spliced ​​to realize the non-planar orbit transfer strategy based on the suspension orbit under the continuous normal force. The m...

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Abstract

The invention discloses a method for realizing fast moving of non-coplanar orbits by utilizing a suspension orbit. The method is realized through moving process planning, moving price analysis and contrast, stability analysis and a multi-pulse manner; and through related simulated analysis, the feasibility and advantages of the method for serving as a non-coplanar orbit moving manner are verified. According to the method, the suspension orbit is used as a middle transfer orbit; and through reasonable design aiming at tasks, the synchronous adjustment of the orbit surface and phase angle can be realized, so that the engine thrust demand is greatly reduced, the task time consumption is saved, benefit is brought to realize the large-range moving tasks in future space, and technical support is provided for the large-range rapid orbit moving tasks.

Description

【Technical field】 [0001] The invention belongs to the field of orbital mechanics, and relates to a method for realizing rapid maneuvering on different-plane orbits by using a suspended orbit. 【Background technique】 [0002] In today's aerospace field, space maneuver is the foundation and core enabling technology of space operations. Future spacecraft must have fast, accurate, autonomous and large-scale orbit maneuver capabilities, which are the basic needs of all complex space missions. Therefore, systematically studying orbit transfer, rendezvous, interception and orbit design and optimization is a key issue to solve long-range large-scale rapid space maneuver and complex tasks. At present, most of the research in engineering practice is limited to the phase adjustment problem of maneuvering between coplanar orbits. However, in order to better realize large-scale maneuvering in space, the problem of rapid maneuvering between different orbits is still to be solved. [0003]...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/20G06F2119/06G06F2119/12
Inventor 罗建军姚玮袁建平朱战霞马卫华唐歌实胡松杰李革非
Owner NORTHWESTERN POLYTECHNICAL UNIV
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